the space shuttle thermal protection system daniel kwon
TRANSCRIPT
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The Space Shuttle Thermal Protection System
Daniel Kwon
16.885J Final Presentation December 6, 2005
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2Space Shuttle Thermal Protection System
Outline
� Requirements and design � TPS performance and evaluation � New requirements � Maintenance techniques � New technology � Conclusions
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3Space Shuttle Thermal Protection System
TPS requirements
� Orbiter structure temperature < 350° F � Reusable for 100 missions � Maintain integrity � Acceptable aerodynamic surface � Minimal weight, maintenance, and
refurbishment
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4Space Shuttle Thermal Protection System
Design summary: Ceramic Tiles
� High purity silicon �
�
� Reaction cured glass (RCG) coating � SIP � Room Temperature
Vulcanizer (RTV) � Gap Fillers
HRSI – black LRSI – white
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5Space Shuttle Thermal Protection System
Design summary: RCC
� Leading edge structure system (LESS) and nose cap � All-carbon composite: rayon cloth graphitized &
impregnated with resin polymer � Regions of orbiter > 2300° F
� Operational temp. of -200 to 3000° F
� LESS consists of 22 RCC panels
� RCC parts form a hollow shell Æ internal radiation
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6Space Shuttle Thermal Protection System
Performance Summary
� Overall, measured surface temperatures lower than requirement, and lower than predicted
� Some areas of excessive tile-to-tile heating (gap filler fix)
� Excellent mechanical performance �
� Recommend similar system (SIP, RTV) for future designs
Test phase: no tiles from underneath detached, small amount of damage to tiles, some LRSI tiles fell off
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7Space Shuttle Thermal Protection System
Evaluation
� Positive aspects � Extremely good thermal performance � Reusable � Ease of maintenance
� Negative aspects � Low impact resistance � Loss of gap fillers (localized heating)
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8Space Shuttle Thermal Protection System
New Requirements
1. Maintain higher amount of structural integrity
2. Tile condition must be easily monitored during a mission
3. TPS must have on-orbit repair capabilities
4. Reduced maintenance to reduce costs
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9Space Shuttle Thermal Protection System
Meeting maintenance requirements
� Challenges: � Large number of components: > 30,000 � Complex tile acceptance logic
New Techniques � On-orbit maintenance �
repair kit (GRABER), SAFER propulsion system, laser topography sensor
� Rapid Re-Waterproofing � Electronic tracking (maintenance)
system
Backflip maneuver, Tile repair kit, RCC
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10Space Shuttle Thermal Protection System
TUFI: Toughened Uni-Piece Fibrous Insulation
� Ceramic tile concept developed by NASA Ames
� Coated with Alumina Enhanced Thermal Barrier (AETB)
� Same SIP, RTV used � 1-2 order of magnitude
more resistant to damage � Maximum operational
temp = 2500° F
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11Space Shuttle Thermal Protection System
Blanket Insulation: TABI and CRI
� Silica-based blanket type TPS � Upgrades to FRSI � Quilted blankets with integrated ceramic
� Improve strength and outer surface � � Ceramic fiber with Q-fiber felt insulation
� � Ceramic matrix composite
Tailorable Advanced Blanket Insulation (TABI) – NASA Ames
Conformal Reusable Insulation (CRI) - Boeing
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12Space Shuttle Thermal Protection System
Metallic TPS
Lightweight metallic structure enclosing a high-efficiency fibrous insulationARMOR (Adaptable Robust Metallic Operable Reusable) TPS – NASA LaRCInconel honeycomb structure enclosing Saffil insulationMore damage tolerant, but lower operational temperatures
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13Space Shuttle Thermal Protection System
Metallic TPS, con’t
� Several variation of Metallic TPS exist � Honeycomb material � Inconel, Titanium, other alloys
� Insulation layer �
� ° F Saffil, Internal Multiscreen Insulation (IMI)
Operational temperature: 2000 - 2200
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14Space Shuttle Thermal Protection System
Hot Structures
� Metallic primary structure acts as a heat sink � Integrated structure and TPS Æ large mass savings � Progress highly dependant on materials research
and fabrication processes � Operational temperatures ~1500° F � Candidate systems � Gamma Titanium aluminide (TiAl) � Metal matrix composites � Nickel metal foam
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15Space Shuttle Thermal Protection System
Conclusions
� TUFI tile system replaces HRSI � TABI systems used to
upgrade FRSI � No RCC replacement � Metallic TPS have high
future potential � Improved maintenance
techniques currently in practice
current requirements
RCC
High Durability
High Temp.
HRSI LRSI
FRSI
new requirements
TUFI
TABI Hot Structures
Metallic TPS
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16Space Shuttle Thermal Protection System
Interfaces 1: Interactions between shuttle subsystems
� Structures � Aerodynamics � Environmental control system � Guidance, Navigation, & Control � External Tank and Solid Rocket
Boosters